| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 060786000 | Combined with starting feature | 30 |
| 20120159964 | ACCESSORY GEARBOX WITH A STARTER/GENERATOR - An assembly for a gas turbine engine comprising an accessory gearbox comprising a drive gear and pinion gear and a starter/generator mechanically mounted to the accessory gearbox. The starter/generator comprising a housing and a portion of a rotatable shaft with a safety disconnect where the safety disconnect is located within the housing of the starter/generator. | 06-28-2012 |
| 20130074516 | GAS TURBINES - A gas turbine engine arrangement comprising a first engine section ( | 03-28-2013 |
| 20120216549 | SYSTEM, PROPULSION SYSTEM AND VEHICLE - One embodiment of the present invention is a unique vehicle. Another embodiment is a unique propulsion system. Yet another embodiment is a unique system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for vehicle propulsions systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 08-30-2012 |
| 20090211260 | Multi-Spool Intercooled Recuperated Gas Turbine - A method and apparatus are disclosed for a gas turbine power plant with a variable area turbine nozzle and an integrated motor/alternator device for starting the gas turbine and power extraction after starting. | 08-27-2009 |
| 20110056212 | SYSTEM AND METHOD FOR APPLYING ENERGY EXTERNALLY FOR FUEL GAS FOR DEW POINT HEATING IN GAS TURBINE POWER PLANT - In a gas turbine power plant, pressurized fuel gas undergoes pressure reduction and gas expansion before being provided to a gas turbine. Condensations, which can damage the turbine, can form as the fuel gas cools when the fuel gas undergoes the pressure reduction and expansion. An electric startup heater is used to superheat the fuel gas to substantially prevent the condensations from forming. The electric startup heater includes band heaters wrapped externally to a fuel gas pipe to heat the fuel gas from outside in. Compared to conventional heaters which provide superheating through internal heating elements, the electric startup heater reduces costs and provides increased safety, flexibility, operational efficiency and ability to adapt to varying fuel gas characteristics. | 03-10-2011 |
| 20110030385 | PROPULSION UNIT - A turboprop propulsion unit for an aircraft comprises a propeller | 02-10-2011 |
| 20120167590 | AIRCRAFT AND GAS TURBINE ENGINE - One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and gas turbine engine powered aircraft. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 07-05-2012 |
| 20120260668 | Combined Cycle Power Plant - A combined cycle power plant is provided and includes a gas turbine engine to generate power, a heat recovery steam generator (HRSG) to produce steam from high energy fluids produced from the generation of power in the gas turbine engine, a steam turbine engine to generate additional power from the steam produced in the HRSG and a thermal load reduction system to reduce thermal loading of components of the HRSG and/or the steam turbine engine during at least startup and/or part load operations, which includes an eductor by which a mixture of compressor discharge air and entrained ambient air is injectable into the HRSG and/or an attemperator to cool superheated steam to be transmitted to the steam turbine engine. | 10-18-2012 |
| 060787000 | Separate device or motive fluid source | 20 |
| 20100162723 | GAS TURBINE ENGINE SHAFT COUPLER - A gas turbine engine is provided that includes a gearbox operable to selectively couple a relatively high pressure spool shaft to a relatively low pressure spool shaft. In one form the gearbox includes a cone clutch that engages a male member of the cone clutch to a female member of the cone clutch during an engine start of the gas turbine engine. A relatively high pressure of a working fluid can be used to bring the male member and the female member together. A spring can also be used to urge the male member and the female member apart when the working fluid is at a relatively low pressure. | 07-01-2010 |
| 20130061601 | CONTROL APPARATUS FOR ANGLING GUIDE VANES OF A TORQUE CONVERTER - A control apparatus for angling guide vanes of a torque converter is provided and includes a modeling unit configured to receive current condition data, to determine a current input power supplied by a starting motor from the current condition data and to output a result of the determination as a control signal and a controller, which is coupled to the modeling unit and thereby receptive of the control signal. The controller is configured to execute a comparison of the current input power with a rating of the starting motor and to angle the guide vanes of the torque converter at an angle in accordance with a result of the comparison. | 03-14-2013 |
| 20110296846 | AERONAUTICAL ENGINE WITH COOLING OF AN ELECTRIC STARTING DEVICE - An aeronautical engine including a fuel pumping device including a high pressure fuel pump including an inlet connected to a low pressure fuel conduit and an outlet connected to a main circuit for feeding high pressure fuel, an electric device starting the engine, and a device cooling the electric starting device connected to the pumping device to ensure cooling by circulation of fuel. The cooling device is supplied with fuel by a pump that includes an inlet connected to the pumping device, upstream from the high pressure pump, and that is driven by an electric motor independently of the high pressure pump. | 12-08-2011 |
| 20100170266 | METHOD AND APPARATUS FOR CONTROLLING A HEATING VALUE OF A LOW ENERGY FUEL - In an embodiment, a method includes determining a first heating value of a low BTU fuel, determining a target fuel quality level based on a state of a turbine system, controlling a second heating value of a high BTU fuel, and injecting the high BTU fuel into the low BTU fuel to achieve the target fuel quality level. | 07-08-2010 |
| 20090145135 | TURBINE BLOW DOWN STARTER FOR TURBINE ENGINE - In order to start a turbine engine ( | 06-11-2009 |
| 20090007568 | EMERGENCY POWER ENGINE RESTART SYSTEM - An engine starting apparatus and method may allow for two methods of engine start where only one engine gearbox accessory pad exists off the aircraft engine. A gearbox lubricating apparatus may also be provided to lubricate the gearbox at altitude without added complexity. Two engine starting inputs (for example, one input for ground start and one input for in-flight engine start) are provided while avoiding complex gearbox designs. Clutches may also be used to prevent the starter gearbox from continuous operation (rotation) after the engine has started. Apparatus and methods are also provided for improving the air-fuel combustion of the hot-gas turbine start input (for in-flight engine start) to minimize the build-up of solid carbon (soot) in and around the combustor and turbine nozzle flow passages. | 01-08-2009 |
| 20100192594 | COMPRESSED AIR STARTER FOR TURBOMACHINE - Air starter for turbomachine, comprising a forward casing ( | 08-05-2010 |
| 20090126369 | Integrated direct drive starter/generator for turbines - A turbine starter/generator machine for a turbine, said turbine comprising: at least one fan blade; at least one turbine enclosure; said starter/generator machine comprising: at least one rotor having rotor elements; at least one stator having stator elements; wherein said stator elements are mounted on said at least one air duct and said rotor elements are mounted on said at least one fan blade; whereby said stator elements magnetically interact with said rotor elements. | 05-21-2009 |
| 060788000 | Starter motor mechanically coupled to power plant | 12 |
| 20130091863 | PLANET GEAR FOR AIR TURBINE STARTER SYSTEM - A planet gear for use in an air turbine starter is formed of a first part having a set of gear teeth at a first axial location. A shaft extends axially away from the first set of gear teeth. A second part is interference fit on the first part, with the second part having a second set of gear teeth. The second part is mounted on the shaft of the first part. An outer diameter of the shaft is selected to be significantly larger than an inner diameter of a cylindrical portion of the second part which is interference fit on the shaft. A ratio of the outer diameter to the inner diameter is between 1.0005 and 1.0100. A planetary gear system, an air turbine starter and a method of installing a planet gear are also disclosed. | 04-18-2013 |
| 20100077769 | STARTER DRIVE ASSEMBLY AND METHOD OF STARTING A GAS TURBINE ENGINE - A starter drive assembly includes a starter output shaft having a plurality of circumferentially-spaced axial grooves, a clutch assembly, and a barrel assembly. The clutch assembly includes a clutch plate configured to engage the axially grooves of the output shaft such that the output shaft and the clutch plate rotate together during a gas turbine engine starting operation. The clutch assembly further includes a screw shaft selectively matingly couplable to the clutch plate, wherein the screw shaft is configured to engage the clutch plate during rotation in a first direction and disengage the clutch plate in a second direction such that the screw shaft and the clutch plate rotate together in the first direction. The barrel assembly includes a first end configured to threadably engage the screw shaft, and a second end that includes a pinion gear configured to engage the ring gear during the gas turbine engine starting operation. | 04-01-2010 |
| 20090120100 | Starter Generator System for a Tip Turbine Engine - A starter-generator system for a tip turbine engine includes a starter motor with a fixed starter generator stator and a starter generator rotor. The fixed starter generator stator is mounted to a static inner support housing. The starter generator rotor surrounds the fixed starter generator stator and is engagement with the axial compressor rotor. | 05-14-2009 |
| 20090199567 | DECOUPLER DEVICES TO PREVENT BACKDRIVE IN AIR TURBINE STARTERS - An air turbine starter for starting an engine includes a housing, and a flow path communicating a flow of gas therethrough; a turbine member; a clutch; and a decoupler device at least partially housed within the output member of the clutch. The decoupler device includes a first shaft portion coupled to and rotating with the output member and a second shaft portion coupled to and rotating with the engine. The first and second shaft portions are axially aligned and configured to engage each another for rotation in a first direction and to separate from each other in a second direction to decouple the output member of the clutch from the engine. The starter further includes a bearing between the inner surface of the output member and the second shaft portion for reducing friction between the second shaft portion and the inner surface of the output member when the first and second shaft portions are decoupled. | 08-13-2009 |
| 20120067062 | TURBINE STARTER VALVE - A turbine starter including a valve to modulate an amount of air permitted to flow to a turbine section, a sensor to detect a characteristic of the air at locations defined between the valve and the turbine section and downstream from the turbine section and an electrically powered motor coupled to the valve and the sensor to control the valve to modulate the amount of the air permitted to flow to the turbine section in accordance with the detected characteristic. | 03-22-2012 |
| 20120266606 | AIR TURBINE START SYSTEM WITH MONOPOLE STARTER AIR VALVE POSITION - An air turbine start system is provided that includes an air turbine starter, a starter air valve, a turbine speed sensor, and a circuit. The starter air valve is movable between an open position, in which the pressurized air may flow into the air turbine starter, and a closed position, in which pressurized air does not flow into the air turbine starter. The turbine speed sensor is coupled to the air turbine starter, and is configured to sense the rotational speed of the turbine and supply a rotational speed signal representative thereof. The circuit is coupled to receive the rotational speed signal and is configured, upon receipt thereof, to determine whether the starter air valve is in the closed position or an open position. | 10-25-2012 |
| 20110252807 | ACCESSORY GEARBOX WITH A STARTER/GENERATOR - An assembly for a gas turbine engine comprising an accessory gearbox comprising a drive gear and a starter/generator mechanically mounted to the accessory gearbox. The starter/generator comprising a rotatable shaft, a pinion gear carried by the shaft, a main machine carried by the shaft, a permanent magnet generator (PMG) carried by the shaft and an exciter carried by the shaft. | 10-20-2011 |
| 20100024434 | Gas turbine engine arrangement - A gas turbine engine arrangement ( | 02-04-2010 |
| 20120042659 | AIR TURBINE STARTER INLET HOUSING ASSEMBLY AIRFLOW PATH - An inlet housing assembly for an Air Turbine Starter includes an outer flowpath curve of an inlet flowpath defined by a multiple of arcuate surfaces in cross-section. | 02-23-2012 |
| 20120111022 | COMBINED AIR TURBINE STARTER, AIR-OIL COOLER, AND FAN - An air turbine starter assembly includes a starter turbine housing having a turbine gas flow path and a fan gas flow path, and a shaft rotatable with respect to the starter turbine housing. A plurality of turbine blades are connected to the shaft. A plurality of fan blades are also connected to the shaft. | 05-10-2012 |
| 20120210728 | Fluid Flow Devices with Vertically Simple Geometry and Methods of Making the Same - A micro-turbine engine, consisting of at least a compressor, combustor, and turbine, is a complicated fluid flow device that controls the flow rate and thermodynamic properties of a working fluid in order to generate shaft power. Existing micro-turbines are costly to manufacture because they are designed with sophisticated contours and exotic materials. The present invention discloses a method for designing a micro-turbine with stacked layers of structure, each of which is designed with vertically simple geometry such that it can be manufactured using conventional machining technology. The resulting micro-turbine is low cost compared to existing alternatives in the target range of power outputs and applications. The present invention also describes a method for connecting the micro-turbine to an electrical generator to generate power. Lastly, the method for designing the micro-turbine is applied to heat exchangers, Rankine engines, fluid mixers, and other fluid flow devices. | 08-23-2012 |
| 20110225978 | TURBOMACHINE DRIVE ARRANGEMENT - An example arrangement for driving a turbomachine includes an input shaft that is configured to rotate a rotor of the turbomachine through a hydraulic log and gear differential rotatable coupled to the input shaft. A motor-generator is rotatably coupled to the differential. The motor-generator has a motor mode of operation and a generator mode of operation. The motor-generator is configured to drive the input shaft through the hydraulic log and differential when the motor-generator is in the motor mode of operation. The input shaft is configured to drive the motor-generator through the hydraulic log and differential when the motor-generator is in the generator mode of operation. | 09-22-2011 |
| 060790000 | Having condition responsive fuel control | 2 |
| 20100132368 | ECOLOGY VALVE FUEL RETURN SYSTEM OPERABLE IN FLUID ISOLATION DURING GAS TURBINE ENGINE SHUT-DOWN - In one embodiment, an ecology valve (EV) fuel return system includes a housing assembly, an ecology valve, and a fuel routing assembly. The ecology valve includes an EV piston slidably disposed within the housing assembly for movement between a fuel storage position and a fuel return position, a fuel storage chamber defined by the EV piston and the housing assembly, and an EV control chamber defined by the EV piston and the housing assembly. The fuel routing assembly, which is fluidly coupled to the EV control chamber and to the fuel storage chamber, is configured to route fuel: (i) from the fuel storage chamber to a fuel supply system when a gas turbine engine (GTE) is in a start-up mode, and (ii) from the first fuel manifold and from the EV control chamber to the fuel storage chamber when the GTE is in a shut-down mode. | 06-03-2010 |
| 20080271461 | METHOD OF STARTING TURBINE ENGINE FROM LOW ENGINE SPEED - A method of starting a turbine engine at a first engine speed value which is lower than a second engine speed value designed for a normal engine starting operation, comprises varying a fuel flow into a combustor of the engine to start the engine in repeatedly alternating speed acceleration and deceleration cycles in order to create an engine speed augmentation in each of the speed acceleration and deceleration cycles, thereby achieving the second engine speed value while preventing the engine from being overheated, and then beginning the normal engine starting operation | 11-06-2008 |
